guest ::
| Home > Publications database > Potentielle Meßtechniken bei thermomechanischen Qualifikationstests an heißen Raumfahrtstrukturen |
| Home > Publications database > Potentielle Meßtechniken bei thermomechanischen Qualifikationstests an heißen Raumfahrtstrukturen |
| Book/Report | FZJ-2018-07014 |
; ;
1994
Forschungszentrum Jülich GmbH Zentralbibliothek, Verlag
Jülich
Please use a persistent id in citations: http://hdl.handle.net/2128/20292
Report No.: Juel-2971
Abstract: The aim of this work is the establishment of measurement technologies for temperature, displacement and strain measurement for the use in thermo-mechanical qualification tests at hot space structures. For the temperature measurement, the use of thermocouples for surface temperature measurement of ceramic matrix composites, based on C and SiC was investigated and optimized concerning chemical compatibility, fixation and ageing behaviour at temperatures up to 1600°C inair and N$_{2}$-atmosphere at 10$^{-2}$ mbar and 10$^{-3}$ mbar. For the non-contacting temperature measurement, a new pyrometric system including on-line emissivity measurement and multireflexion compensation was optimized and qualified for the temperature range between 700°C and 1600°C. In combination with this pyrometric system, a new thermocouple calibration method was developed and patented which allows a calibration even above 1700°C. Additionally, the use of high temperature strain gauges applied at ceramic matrix composites was optimized and qualified for application temperatures up to 1000°C. Detailed investigations were performed concerning chemical compatibility, service life and measurement accuracy. For the temperature range up to 1600°C, a high temperature extensometer was developed and patented, which allows a relative movement compensation of the measurement object. An additionally developed and patented high temperature displacement measurement sensor allows a displacement measurement up to the surface temperatures of 1400°C. With the investigated and qualified HT-measurement technologies, the necessary requirements for the component qualification of the hot structures of the space plane HERMES for limit reentry conditions (T$_{max}$: 1600°C) can be fulfilled.
|
The record appears in these collections: |
PDF
PDF (PDFA)